推力故障下运载火箭剩余能力可达域评估方法

Assessment Method for Reachable Domain of Residual Capability of Launch Vehicle under Thrust Fault

摘要

任务重规划是提高液体运载火箭容错能力,进而提升全箭可靠性/安全性的关键技术,该技术旨在突发故障后,规划出与运载火箭剩余能力匹配的新弹道,以减小故障影响。因此,对剩余能力的准确评估是实现最优重规划决策的基础。为量化运载火箭剩余能力,将常用于量化在轨航天器和再入飞行器能力的可达域概念,进一步拓展到连续推力控制、执行入轨任务的运载火箭。结合航天发射任务特点,提出了一种基于分层降维思想的高维可达域表征方案。通过求解几类弹道优化问题,获得高维复杂的运载火箭可达域数值解。针对弹道优化问题中的强非线性和非凸入轨约束,采用辅助滑行段和标量动力学方程,实现了入轨约束的无损凸化,为通过凸优化方法实现高效可达域计算奠定了基础。以执行低地球轨道任务的运载火箭为例,针对其在末级飞行段的推力下降故障情况后的可达域进行仿真。结果表明,提出的剩余能力可达域评估方法能准确表征运载火箭故障后的轨道面可达域和轨道面内可达域,实现对故障后剩余能力的全面量化评估,从而为最优重规划决策提供支撑。

Abstract

Mission re-planning is a critical technology for enhancing the fault tolerance of liquid-propellant launch vehicle, thus improving the reliability and safety. Its objective is to generate feasible trajectories align with the vehicle's residual capabilities following a propulsion system fault. Accurate assessment of residual capability forms the foundation for optimal re-planning decisions. To quantify the residual capability, the reachable domain concept, which is conventionally applied to orbital spacecraft and reentry vehicles, was extended to launch vehicles. Utilizing unique characteristics of space launch operations, a hierarchical dimension-reduction framework for high-dimensional reachable domain characterization was proposed. The numerical solution can be obtained by decomposing complex high-dimensional reachable domain into several trajectory optimization subproblems. The auxiliary coasting phases and the scalar-state dynamic equations were developed to achieve lossless convexification of the strongly nonlinear and non-convex orbit injection constraints in trajectory optimization, establishing the theoretical foundation for efficient reachable domain computation via convex optimization. Taking a low Earth orbit mission as a case study, various thrust drop fault scenarios during the upper-stage flight phase were simulated, and their corresponding reachable domains were computed. Results demonstrate that the proposed method effectively characterizes both the orbital plane and in-plane reachable domains, enabling comprehensive quantitative assessment of residual capabilities to support optimal re-planning decisions.

关键词

运载火箭 / 任务重规划 / 可达域 / 推力故障 / 凸优化

Key words

launch vehicle / mission re-planning / reachable domain / thrust fault / convex optimization

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